/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/*
  24 state EKF based on https://github.com/priseborough/InertialNav

  Converted from Matlab to C++ by Paul Riseborough

  This program is free software: you can redistribute it and/or modify
  it under the terms of the GNU General Public License as published by
  the Free Software Foundation, either version 3 of the License, or
  (at your option) any later version.

  This program is distributed in the hope that it will be useful,
  but WITHOUT ANY WARRANTY; without even the implied warranty of
  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
  GNU General Public License for more details.

  You should have received a copy of the GNU General Public License
  along with this program.  If not, see <http://www.gnu.org/licenses/>.
 */

#ifndef AP_NavEKF2_core
#define AP_NavEKF2_core

#pragma GCC optimize("O3")

// #define MATH_CHECK_INDEXES 1
// #define EK2_DISABLE_INTERRUPTS 1


#include <AP_Math/AP_Math.h>
#include "AP_NavEKF2.h"

#include <AP_Math/vectorN.h>

// GPS pre-flight check bit locations
#define MASK_GPS_NSATS      (1<<0)
#define MASK_GPS_HDOP       (1<<1)
#define MASK_GPS_SPD_ERR    (1<<2)
#define MASK_GPS_POS_ERR    (1<<3)
#define MASK_GPS_YAW_ERR 	(1<<4)
#define MASK_GPS_POS_DRIFT  (1<<5)
#define MASK_GPS_VERT_SPD   (1<<6)
#define MASK_GPS_HORIZ_SPD  (1<<7)

/*
 * IMU FIFO buffer length depends on the IMU update rate being used and the maximum sensor delay
 * Samples*delta_time must be > max sensor delay
*/
#if APM_BUILD_TYPE(APM_BUILD_ArduCopter)
#define IMU_BUFFER_LENGTH       104 // maximum 260 msec delay at 400 Hz
#elif APM_BUILD_TYPE(APM_BUILD_APMrover2)
#define IMU_BUFFER_LENGTH       13 // maximum 260 msec delay at 50 Hz
#elif APM_BUILD_TYPE(APM_BUILD_ArduPlane)
#define IMU_BUFFER_LENGTH       13 // maximum 260 msec delay at 50 Hz
#else
#define IMU_BUFFER_LENGTH       104 // unknown so use max buffer length
#endif

class AP_AHRS;

class NavEKF2_core
{
public:
    // Constructor
    NavEKF2_core(NavEKF2 &frontend, const AP_AHRS *ahrs, AP_Baro &baro, const RangeFinder &rng);

    // Initialise the states from accelerometer and magnetometer data (if present)
    // This method can only be used when the vehicle is static
    bool InitialiseFilterBootstrap(void);

    // Update Filter States - this should be called whenever new IMU data is available
    void UpdateFilter(void);

    // Check basic filter health metrics and return a consolidated health status
    bool healthy(void) const;

    // Return the last calculated NED position relative to the reference point (m).
    // If a calculated solution is not available, use the best available data and return false
    // If false returned, do not use for flight control
    bool getPosNED(Vector3f &pos) const;

    // return NED velocity in m/s
    void getVelNED(Vector3f &vel) const;

    // Return the rate of change of vertical position in the down diection (dPosD/dt) in m/s
    // This can be different to the z component of the EKF velocity state because it will fluctuate with height errors and corrections in the EKF
    // but will always be kinematically consistent with the z component of the EKF position state
    float getPosDownDerivative(void) const;

    // This returns the specific forces in the NED frame
    void getAccelNED(Vector3f &accelNED) const;

    // return body axis gyro bias estimates in rad/sec
    void getGyroBias(Vector3f &gyroBias) const;

    // return body axis gyro scale factor error as a percentage
    void getGyroScaleErrorPercentage(Vector3f &gyroScale) const;

    // return tilt error convergence metric
    void getTiltError(float &ang) const;

    // reset body axis gyro bias estimates
    void resetGyroBias(void);

    // Resets the baro so that it reads zero at the current height
    // Resets the EKF height to zero
    // Adjusts the EKf origin height so that the EKF height + origin height is the same as before
    // Returns true if the height datum reset has been performed
    // If using a range finder for height no reset is performed and it returns false
    bool resetHeightDatum(void);

    // Commands the EKF to not use GPS.
    // This command must be sent prior to arming as it will only be actioned when the filter is in static mode
    // This command is forgotten by the EKF each time it goes back into static mode (eg the vehicle disarms)
    // Returns 0 if command rejected
    // Returns 1 if attitude, vertical velocity and vertical position will be provided
    // Returns 2 if attitude, 3D-velocity, vertical position and relative horizontal position will be provided
    uint8_t setInhibitGPS(void);

    // return the horizontal speed limit in m/s set by optical flow sensor limits
    // return the scale factor to be applied to navigation velocity gains to compensate for increase in velocity noise with height when using optical flow
    void getEkfControlLimits(float &ekfGndSpdLimit, float &ekfNavVelGainScaler) const;

    // return the Z-accel bias estimate in m/s^2
    void getAccelZBias(float &zbias) const;

    // return the NED wind speed estimates in m/s (positive is air moving in the direction of the axis)
    void getWind(Vector3f &wind) const;

    // return earth magnetic field estimates in measurement units / 1000
    void getMagNED(Vector3f &magNED) const;

    // return body magnetic field estimates in measurement units / 1000
    void getMagXYZ(Vector3f &magXYZ) const;

    // Return estimated magnetometer offsets
    // Return true if magnetometer offsets are valid
    bool getMagOffsets(Vector3f &magOffsets) const;

    // Return the last calculated latitude, longitude and height in WGS-84
    // If a calculated location isn't available, return a raw GPS measurement
    // The status will return true if a calculation or raw measurement is available
    // The getFilterStatus() function provides a more detailed description of data health and must be checked if data is to be used for flight control
    bool getLLH(struct Location &loc) const;

    // return the latitude and longitude and height used to set the NED origin
    // All NED positions calculated by the filter are relative to this location
    // Returns false if the origin has not been set
    bool getOriginLLH(struct Location &loc) const;

    // set the latitude and longitude and height used to set the NED origin
    // All NED positions calcualted by the filter will be relative to this location
    // The origin cannot be set if the filter is in a flight mode (eg vehicle armed)
    // Returns false if the filter has rejected the attempt to set the origin
    bool setOriginLLH(struct Location &loc);

    // return estimated height above ground level
    // return false if ground height is not being estimated.
    bool getHAGL(float &HAGL) const;

    // return the Euler roll, pitch and yaw angle in radians
    void getEulerAngles(Vector3f &eulers) const;

    // return the transformation matrix from XYZ (body) to NED axes
    void getRotationBodyToNED(Matrix3f &mat) const;

    // return the quaternions defining the rotation from NED to XYZ (body) axes
    void getQuaternion(Quaternion &quat) const;

    // return the innovations for the NED Pos, NED Vel, XYZ Mag and Vtas measurements
    void  getInnovations(Vector3f &velInnov, Vector3f &posInnov, Vector3f &magInnov, float &tasInnov, float &yawInnov) const;

    // return the innovation consistency test ratios for the velocity, position, magnetometer and true airspeed measurements
    void  getVariances(float &velVar, float &posVar, float &hgtVar, Vector3f &magVar, float &tasVar, Vector2f &offset) const;

    // should we use the compass? This is public so it can be used for
    // reporting via ahrs.use_compass()
    bool use_compass(void) const;

    // write the raw optical flow measurements
    // rawFlowQuality is a measured of quality between 0 and 255, with 255 being the best quality
    // rawFlowRates are the optical flow rates in rad/sec about the X and Y sensor axes.
    // rawGyroRates are the sensor rotation rates in rad/sec measured by the sensors internal gyro
    // The sign convention is that a RH physical rotation of the sensor about an axis produces both a positive flow and gyro rate
    // msecFlowMeas is the scheduler time in msec when the optical flow data was received from the sensor.
    void  writeOptFlowMeas(uint8_t &rawFlowQuality, Vector2f &rawFlowRates, Vector2f &rawGyroRates, uint32_t &msecFlowMeas);

    // return data for debugging optical flow fusion
    void getFlowDebug(float &varFlow, float &gndOffset, float &flowInnovX, float &flowInnovY, float &auxInnov, float &HAGL, float &rngInnov, float &range, float &gndOffsetErr) const;

    // called by vehicle code to specify that a takeoff is happening
    // causes the EKF to compensate for expected barometer errors due to ground effect
    void setTakeoffExpected(bool val);

    // called by vehicle code to specify that a touchdown is expected to happen
    // causes the EKF to compensate for expected barometer errors due to ground effect
    void setTouchdownExpected(bool val);

    /*
    return the filter fault status as a bitmasked integer
     0 = quaternions are NaN
     1 = velocities are NaN
     2 = badly conditioned X magnetometer fusion
     3 = badly conditioned Y magnetometer fusion
     5 = badly conditioned Z magnetometer fusion
     6 = badly conditioned airspeed fusion
     7 = badly conditioned synthetic sideslip fusion
     7 = filter is not initialised
    */
    void  getFilterFaults(uint8_t &faults) const;

    /*
    return filter timeout status as a bitmasked integer
     0 = position measurement timeout
     1 = velocity measurement timeout
     2 = height measurement timeout
     3 = magnetometer measurement timeout
     5 = unassigned
     6 = unassigned
     7 = unassigned
     7 = unassigned
    */
    void  getFilterTimeouts(uint8_t &timeouts) const;

    /*
    return filter gps quality check status
    */
    void  getFilterGpsStatus(nav_gps_status &status) const;

    /*
    Return a filter function status that indicates:
        Which outputs are valid
        If the filter has detected takeoff
        If the filter has activated the mode that mitigates against ground effect static pressure errors
        If GPS data is being used
    */
    void  getFilterStatus(nav_filter_status &status) const;

    // send an EKF_STATUS_REPORT message to GCS
    void send_status_report(mavlink_channel_t chan);

    // provides the height limit to be observed by the control loops
    // returns false if no height limiting is required
    // this is needed to ensure the vehicle does not fly too high when using optical flow navigation
    bool getHeightControlLimit(float &height) const;

    // return the amount of yaw angle change due to the last yaw angle reset in radians
    // returns the time of the last yaw angle reset or 0 if no reset has ever occurred
    uint32_t getLastYawResetAngle(float &yawAng);

private:
    // Reference to the global EKF frontend for parameters
    NavEKF2 &frontend;

    typedef float ftype;
#if defined(MATH_CHECK_INDEXES) && (MATH_CHECK_INDEXES == 1)
    typedef VectorN<ftype,2> Vector2;
    typedef VectorN<ftype,3> Vector3;
    typedef VectorN<ftype,4> Vector4;
    typedef VectorN<ftype,5> Vector5;
    typedef VectorN<ftype,6> Vector6;
    typedef VectorN<ftype,7> Vector7;
    typedef VectorN<ftype,8> Vector8;
    typedef VectorN<ftype,9> Vector9;
    typedef VectorN<ftype,10> Vector10;
    typedef VectorN<ftype,11> Vector11;
    typedef VectorN<ftype,13> Vector13;
    typedef VectorN<ftype,14> Vector14;
    typedef VectorN<ftype,15> Vector15;
    typedef VectorN<ftype,22> Vector22;
    typedef VectorN<ftype,23> Vector23;
    typedef VectorN<ftype,24> Vector24;
    typedef VectorN<ftype,25> Vector25;
    typedef VectorN<ftype,31> Vector31;
    typedef VectorN<ftype,28> Vector28;
    typedef VectorN<VectorN<ftype,3>,3> Matrix3;
    typedef VectorN<VectorN<ftype,24>,24> Matrix24;
    typedef VectorN<VectorN<ftype,34>,50> Matrix34_50;
    typedef VectorN<uint32_t,50> Vector_u32_50;
#else
    typedef ftype Vector2[2];
    typedef ftype Vector3[3];
    typedef ftype Vector4[4];
    typedef ftype Vector5[5];
    typedef ftype Vector6[6];
    typedef ftype Vector7[7];
    typedef ftype Vector8[8];
    typedef ftype Vector9[9];
    typedef ftype Vector10[10];
    typedef ftype Vector11[11];
    typedef ftype Vector13[13];
    typedef ftype Vector14[14];
    typedef ftype Vector15[15];
    typedef ftype Vector22[22];
    typedef ftype Vector23[23];
    typedef ftype Vector24[24];
    typedef ftype Vector25[25];
    typedef ftype Vector28[28];
    typedef ftype Matrix3[3][3];
    typedef ftype Matrix24[24][24];
    typedef ftype Matrix34_50[34][50];
    typedef uint32_t Vector_u32_50[50];
#endif

    const AP_AHRS *_ahrs;
    AP_Baro &_baro;
    const RangeFinder &_rng;

    // the states are available in two forms, either as a Vector31, or
    // broken down as individual elements. Both are equivalent (same
    // memory)
    Vector28 statesArray;
    struct state_elements {
        Vector3f    angErr;         // 0..2
        Vector3f    velocity;       // 3..5
        Vector3f    position;       // 6..8
        Vector3f    gyro_bias;      // 9..11
        Vector3f    gyro_scale;     // 12..14
        float       accel_zbias;    // 15
        Vector3f    earth_magfield; // 16..18
        Vector3f    body_magfield;  // 19..21
        Vector2f    wind_vel;       // 22..23
        Quaternion  quat;           // 24..27
    } &stateStruct;

    struct output_elements {
        Quaternion  quat;           // 0..3
        Vector3f    velocity;       // 4..6
        Vector3f    position;       // 7..9
    };

    struct imu_elements {
        Vector3f    delAng;         // 0..2
        Vector3f    delVel;         // 3..5
        float       delAngDT;       // 6
        float       delVelDT;       // 7
        uint32_t    frame;          // 8
        uint32_t    time_ms;        // 9
    };

    struct gps_elements {
        Vector2f    pos;         // 0..1
        float       hgt;         // 2
        Vector3f    vel;         // 3..5
        uint32_t    time_ms;     // 6
    };

    struct mag_elements {
        Vector3f    mag;         // 0..2
        uint32_t    time_ms;     // 3
    };

    struct baro_elements {
        float       hgt;         // 0
        uint32_t    time_ms;     // 1
    };

    struct tas_elements {
        float       tas;         // 0
        uint32_t    time_ms;     // 1
    };

    struct of_elements {
        Vector2f    flowRadXY;      // 0..1
        Vector2f    flowRadXYcomp;  // 2..3
        uint32_t    time_ms;        // 4
    };

    // update the quaternion, velocity and position states using IMU measurements
    void UpdateStrapdownEquationsNED();

    // calculate the predicted state covariance matrix
    void CovariancePrediction();

    // force symmetry on the state covariance matrix
    void ForceSymmetry();

    // copy covariances across from covariance prediction calculation and fix numerical errors
    void CopyCovariances();

    // constrain variances (diagonal terms) in the state covariance matrix
    void ConstrainVariances();

    // constrain states
    void ConstrainStates();

    // fuse selected position, velocity and height measurements
    void FuseVelPosNED();

    // fuse magnetometer measurements
    void FuseMagnetometer();

    // fuse true airspeed measurements
    void FuseAirspeed();

    // fuse sythetic sideslip measurement of zero
    void FuseSideslip();

    // zero specified range of rows in the state covariance matrix
    void zeroRows(Matrix24 &covMat, uint8_t first, uint8_t last);

    // zero specified range of columns in the state covariance matrix
    void zeroCols(Matrix24 &covMat, uint8_t first, uint8_t last);

    // store imu data in the FIFO
    void StoreIMU(void);

    // Reset the stored IMU history to current data
    void StoreIMU_reset(void);

    // recall IMU data from the FIFO
    void RecallIMU();

    // store output data in the FIFO
    void StoreOutput(void);

    // Reset the stored output history to current data
    void StoreOutputReset(void);

    // Reset the stored output quaternion history to current EKF state
    void StoreQuatReset(void);

    // recall output data from the FIFO
    void RecallOutput();

    // store altimeter data
    void StoreBaro();

    // recall altimeter data at the fusion time horizon
    // return true if data found
    bool RecallBaro();

    // store magnetometer data
    void StoreMag();

    // recall magetometer data at the fusion time horizon
    // return true if data found
    bool RecallMag();

    // store GPS data
    void StoreGPS();

    // recall GPS data at the fusion time horizon
    // return true if data found
    bool RecallGPS();

    // store true airspeed data
    void StoreTAS();

    // recall true airspeed data at the fusion time horizon
    // return true if data found
    bool RecallTAS();

    // store optical flow data
    void StoreOF();

    // recall optical flow data at the fusion time horizon
    // return true if data found
    bool RecallOF();

    // calculate nav to body quaternions from body to nav rotation matrix
    void quat2Tbn(Matrix3f &Tbn, const Quaternion &quat) const;

    // calculate the NED earth spin vector in rad/sec
    void calcEarthRateNED(Vector3f &omega, int32_t latitude) const;

    // initialise the covariance matrix
    void CovarianceInit();

    // helper functions for readIMUData
    bool readDeltaVelocity(uint8_t ins_index, Vector3f &dVel, float &dVel_dt);
    bool readDeltaAngle(uint8_t ins_index, Vector3f &dAng);

    // update IMU delta angle and delta velocity measurements
    void readIMUData();

    // check for new valid GPS data and update stored measurement if available
    void readGpsData();

    // check for new altitude measurement data and update stored measurement if available
    void readHgtData();

    // check for new magnetometer data and update store measurements if available
    void readMagData();

    // check for new airspeed data and update stored measurements if available
    void readAirSpdData();

    // determine when to perform fusion of GPS position and  velocity measurements
    void SelectVelPosFusion();

    // determine when to perform fusion of magnetometer measurements
    void SelectMagFusion();

    // determine when to perform fusion of true airspeed measurements
    void SelectTasFusion();

    // determine when to perform fusion of synthetic sideslp measurements
    void SelectBetaFusion();

    // force alignment of the yaw angle using GPS velocity data
    void alignYawGPS();

    // initialise the earth magnetic field states using declination and current attitude and magnetometer meaasurements
    // and return attitude quaternion
    Quaternion calcQuatAndFieldStates(float roll, float pitch);

    // zero stored variables
    void InitialiseVariables();

    // reset the horizontal position states uing the last GPS measurement
    void ResetPosition(void);

    // reset velocity states using the last GPS measurement
    void ResetVelocity(void);

    // reset the vertical position state using the last height measurement
    void ResetHeight(void);

    // return true if we should use the airspeed sensor
    bool useAirspeed(void) const;

    // return true if the vehicle code has requested the filter to be ready for flight
    bool readyToUseGPS(void) const;

    // decay GPS horizontal position offset to close to zero at a rate of 1 m/s
    // this allows large GPS position jumps to be accomodated gradually
    void decayGpsOffset(void);

    // Check for filter divergence
    void checkDivergence(void);

    // Calculate weighting that is applied to IMU1 accel data to blend data from IMU's 1 and 2
    void calcIMU_Weighting(float K1, float K2);

    // return true if optical flow data is available
    bool optFlowDataPresent(void) const;

    // return true if we should use the range finder sensor
    bool useRngFinder(void) const;

    // determine when to perform fusion of optical flow measurements
    void SelectFlowFusion();

    // Estimate terrain offset using a single state EKF
    void EstimateTerrainOffset();

    // fuse optical flow measurements into the main filter
    void FuseOptFlow();

    // Control filter mode changes
    void controlFilterModes();

    // Determine if we are flying or on the ground
    void detectFlight();

    // Set inertial navigaton aiding mode
    void setAidingMode();

    // Determine if learning of wind and magnetic field will be enabled and set corresponding indexing limits to
    // avoid unnecessary operations
    void setWindMagStateLearningMode();

    // Check the alignmnent status of the tilt and yaw attitude
    // Used during initial bootstrap alignment of the filter
    void checkAttitudeAlignmentStatus();

    // Control reset of yaw and magnetic field states
    void controlMagYawReset();

    // Set the NED origin to be used until the next filter reset
    void setOrigin();

    // determine if a takeoff is expected so that we can compensate for expected barometer errors due to ground effect
    bool getTakeoffExpected();

    // determine if a touchdown is expected so that we can compensate for expected barometer errors due to ground effect
    bool getTouchdownExpected();

    // Assess GPS data quality and return true if good enough to align the EKF
    bool calcGpsGoodToAlign(void);

    // update inflight calculaton that determines if GPS data is good enough for reliable navigation
    void calcGpsGoodForFlight(void);

    // Read the range finder and take new measurements if available
    // Apply a median filter to range finder data
    void readRangeFinder();

    // check if the vehicle has taken off during optical flow navigation by looking at inertial and range finder data
    void detectOptFlowTakeoff(void);

    // align the NE earth magnetic field states with the published declination
    void alignMagStateDeclination();

    // Fuse compass measurements using a simple declination observation (doesn't require magnetic field states)
    void fuseCompass();

    // Fuse declination angle to keep earth field declination from changing when we don't have earth relative observations.
    void FuseDeclination();

    // Calculate compass heading innovation
    float calcMagHeadingInnov();

    // Propagate PVA solution forward from the fusion time horizon to the current time horizon
    // using buffered IMU data
    void calcOutputStates();

    // Propagate PVA solution forward from the fusion time horizon to the current time horizon
    // using a simple observer
    void calcOutputStatesFast();

    // Round to the nearest multiple of a integer
    uint32_t roundToNearest(uint32_t dividend, uint32_t divisor );

    // Length of FIFO buffers used for non-IMU sensor data.
    // Must be larger than the maximum number of sensor samples that will arrive during the time period defined by IMU_BUFFER_LENGTH
    // OBS_BUFFER_LENGTH > IMU_BUFFER_LENGTH * dtIMUavg * 'max sensor rate'
    static const uint32_t OBS_BUFFER_LENGTH = 5;

    // Variables
    bool statesInitialised;         // boolean true when filter states have been initialised
    bool velHealth;                 // boolean true if velocity measurements have passed innovation consistency check
    bool posHealth;                 // boolean true if position measurements have passed innovation consistency check
    bool hgtHealth;                 // boolean true if height measurements have passed innovation consistency check
    bool magHealth;                 // boolean true if magnetometer has passed innovation consistency check
    bool tasHealth;                 // boolean true if true airspeed has passed innovation consistency check
    bool velTimeout;                // boolean true if velocity measurements have failed innovation consistency check and timed out
    bool posTimeout;                // boolean true if position measurements have failed innovation consistency check and timed out
    bool hgtTimeout;                // boolean true if height measurements have failed innovation consistency check and timed out
    bool magTimeout;                // boolean true if magnetometer measurements have failed for too long and have timed out
    bool tasTimeout;                // boolean true if true airspeed measurements have failed for too long and have timed out
    bool badMag;                    // boolean true if the magnetometer is declared to be producing bad data
    bool badIMUdata;                // boolean true if the bad IMU data is detected

    float gpsNoiseScaler;           // Used to scale the  GPS measurement noise and consistency gates to compensate for operation with small satellite counts
    Vector28 Kfusion;               // Kalman gain vector
    Matrix24 KH;                    // intermediate result used for covariance updates
    Matrix24 KHP;                   // intermediate result used for covariance updates
    Matrix24 P;                     // covariance matrix
    imu_elements storedIMU[IMU_BUFFER_LENGTH];      // IMU data buffer
    gps_elements storedGPS[OBS_BUFFER_LENGTH];      // GPS data buffer
    mag_elements storedMag[OBS_BUFFER_LENGTH];      // Magnetometer data buffer
    baro_elements storedBaro[OBS_BUFFER_LENGTH];    // Baro data buffer
    tas_elements storedTAS[OBS_BUFFER_LENGTH];      // TAS data buffer
    output_elements storedOutput[IMU_BUFFER_LENGTH];// output state buffer
    Vector3f correctedDelAng;       // delta angles about the xyz body axes corrected for errors (rad)
    Quaternion correctedDelAngQuat; // quaternion representation of correctedDelAng
    Vector3f correctedDelVel;       // delta velocities along the XYZ body axes for weighted average of IMU1 and IMU2 corrected for errors (m/s)
    Vector3f summedDelAng;          // corrected & summed delta angles about the xyz body axes (rad)
    Vector3f summedDelVel;          // corrected & summed delta velocities along the XYZ body axes (m/s)
    Matrix3f prevTnb;               // previous nav to body transformation used for INS earth rotation compensation
    ftype accNavMag;                // magnitude of navigation accel - used to adjust GPS obs variance (m/s^2)
    ftype accNavMagHoriz;           // magnitude of navigation accel in horizontal plane (m/s^2)
    Vector3f earthRateNED;          // earths angular rate vector in NED (rad/s)
    ftype dtIMUavg;                 // expected time between IMU measurements (sec)
    ftype dt;                       // time lapsed since the last covariance prediction (sec)
    ftype hgtRate;                  // state for rate of change of height filter
    bool onGround;                  // true when the flight vehicle is definitely on the ground
    bool prevOnGround;              // value of onGround from previous frame - used to detect transition
    bool inFlight;                  // true when the vehicle is definitely flying
    bool prevInFlight;              // value inFlight from previous frame - used to detect transition
    bool manoeuvring;               // boolean true when the flight vehicle is performing horizontal changes in velocity
    uint32_t airborneDetectTime_ms; // last time flight movement was detected
    Vector6 innovVelPos;            // innovation output for a group of measurements
    Vector6 varInnovVelPos;         // innovation variance output for a group of measurements
    bool fuseVelData;               // this boolean causes the velNED measurements to be fused
    bool fusePosData;               // this boolean causes the posNE measurements to be fused
    bool fuseHgtData;               // this boolean causes the hgtMea measurements to be fused
    Vector3f innovMag;              // innovation output from fusion of X,Y,Z compass measurements
    Vector3f varInnovMag;           // innovation variance output from fusion of X,Y,Z compass measurements
    ftype innovVtas;                // innovation output from fusion of airspeed measurements
    ftype varInnovVtas;             // innovation variance output from fusion of airspeed measurements
    bool covPredStep;               // boolean set to true when a covariance prediction step has been performed
    bool magFusePerformed;          // boolean set to true when magnetometer fusion has been perfomred in that time step
    bool magFuseRequired;           // boolean set to true when magnetometer fusion will be perfomred in the next time step
    uint32_t prevTasStep_ms;        // time stamp of last TAS fusion step
    uint32_t prevBetaStep_ms;       // time stamp of last synthetic sideslip fusion step
    uint32_t lastMagUpdate_us;      // last time compass was updated in usec
    Vector3f velDotNED;             // rate of change of velocity in NED frame
    Vector3f velDotNEDfilt;         // low pass filtered velDotNED
    uint32_t imuSampleTime_ms;      // time that the last IMU value was taken
    bool newDataTas;                // true when new airspeed data has arrived
    bool tasDataWaiting;            // true when new airspeed data is waiting to be fused
    uint32_t lastHgtReceived_ms;    // time last time we received height data
    uint16_t hgtRetryTime_ms;       // time allowed without use of height measurements before a height timeout is declared
    uint32_t lastVelPassTime_ms;    // time stamp when GPS velocity measurement last passed innovation consistency check (msec)
    uint32_t lastPosPassTime_ms;    // time stamp when GPS position measurement last passed innovation consistency check (msec)
    uint32_t lastHgtPassTime_ms;    // time stamp when height measurement last passed innovation consistency check (msec)
    uint32_t lastTasPassTime_ms;    // time stamp when airspeed measurement last passed innovation consistency check (msec)
    uint32_t lastTimeGpsReceived_ms;// last time we recieved GPS data
    uint32_t timeAtLastAuxEKF_ms;   // last time the auxilliary filter was run to fuse range or optical flow measurements
    uint32_t secondLastGpsTime_ms;  // time of second last GPS fix used to determine how long since last update
    uint32_t lastHealthyMagTime_ms; // time the magnetometer was last declared healthy
    uint32_t ekfStartTime_ms;       // time the EKF was started (msec)
    Matrix24 nextP;                 // Predicted covariance matrix before addition of process noise to diagonals
    Vector24 processNoise;          // process noise added to diagonals of predicted covariance matrix
    Vector25 SF;                    // intermediate variables used to calculate predicted covariance matrix
    Vector5 SG;                     // intermediate variables used to calculate predicted covariance matrix
    Vector8 SQ;                     // intermediate variables used to calculate predicted covariance matrix
    Vector23 SPP;                   // intermediate variables used to calculate predicted covariance matrix
    bool yawAligned;                // true when the yaw angle has been aligned
    Vector2f gpsPosGlitchOffsetNE;  // offset applied to GPS data in the NE direction to compensate for rapid changes in GPS solution
    Vector2f lastKnownPositionNE;   // last known position
    uint32_t lastDecayTime_ms;      // time of last decay of GPS position offset
    float velTestRatio;             // sum of squares of GPS velocity innovation divided by fail threshold
    float posTestRatio;             // sum of squares of GPS position innovation divided by fail threshold
    float hgtTestRatio;             // sum of squares of baro height innovation divided by fail threshold
    Vector3f magTestRatio;          // sum of squares of magnetometer innovations divided by fail threshold
    float tasTestRatio;             // sum of squares of true airspeed innovation divided by fail threshold
    bool inhibitWindStates;         // true when wind states and covariances are to remain constant
    bool inhibitMagStates;          // true when magnetic field states and covariances are to remain constant
    bool firstMagYawInit;           // true when the first post takeoff initialisation of earth field and yaw angle has been performed
    bool secondMagYawInit;          // true when the second post takeoff initialisation of earth field and yaw angle has been performed
    Vector2f gpsVelGlitchOffset;    // Offset applied to the GPS velocity when the gltch radius is being  decayed back to zero
    bool gpsNotAvailable;           // bool true when valid GPS data is not available
    bool isAiding;                  // true when the filter is fusing position, velocity or flow measurements
    bool prevIsAiding;              // isAiding from previous frame
    struct Location EKF_origin;     // LLH origin of the NED axis system - do not change unless filter is reset
    bool validOrigin;               // true when the EKF origin is valid
    float gpsSpdAccuracy;           // estimated speed accuracy in m/s returned by the UBlox GPS receiver
    uint32_t lastGpsVelFail_ms;     // time of last GPS vertical velocity consistency check fail
    Vector3f lastMagOffsets;        // magnetometer offsets returned by compass object from previous update
    uint32_t lastGpsAidBadTime_ms;  // time in msec gps aiding was last detected to be bad
    float posDownAtTakeoff;         // flight vehicle vertical position at arming used as a reference point
    bool highYawRate;               // true when the vehicle is doing rapid yaw rotation where gyro scale factor errors could cause loss of heading reference
    float yawRateFilt;              // filtered yaw rate used to determine when the vehicle is doing rapid yaw rotation where gyro scel factor errors could cause loss of heading reference
    bool useGpsVertVel;             // true if GPS vertical velocity should be used
    float yawResetAngle;            // Change in yaw angle due to last in-flight yaw reset in radians. A positive value means the yaw angle has increased.
    uint32_t lastYawReset_ms;       // System time at which the last yaw reset occurred. Returned by getLastYawResetAngle
    Vector3f tiltErrVec;            // Vector of most recent attitude error correction from Vel,Pos fusion
    float tiltErrFilt;              // Filtered tilt error metric
    bool tiltAlignComplete;         // true when tilt alignment is complete
    bool yawAlignComplete;          // true when yaw alignment is complete
    uint8_t stateIndexLim;          // Max state index used during matrix and array operations
    imu_elements imuDataDelayed;    // IMU data at the fusion time horizon
    imu_elements imuDataNew;        // IMU data at the current time horizon
    uint8_t fifoIndexNow;           // Global index for inertial and output solution at current time horizon
    uint8_t fifoIndexDelayed;       // Global index for inertial and output solution at delayed/fusion time horizon
    baro_elements baroDataNew;      // Baro data at the current time horizon
    baro_elements baroDataDelayed;  // Baro data at the fusion time horizon
    uint8_t baroStoreIndex;         // Baro data storage index
    tas_elements tasDataNew;        // TAS data at the current time horizon
    tas_elements tasDataDelayed;    // TAS data at the fusion time horizon
    uint8_t tasStoreIndex;          // TAS data storage index
    mag_elements magDataNew;        // Magnetometer data at the current time horizon
    mag_elements magDataDelayed;    // Magnetometer data at the fusion time horizon
    uint8_t magStoreIndex;          // Magnetometer data storage index
    gps_elements gpsDataNew;        // GPS data at the current time horizon
    gps_elements gpsDataDelayed;    // GPS data at the fusion time horizon
    uint8_t gpsStoreIndex;          // GPS data storage index
    output_elements outputDataNew;  // output state data at the current time step
    output_elements outputDataDelayed; // output state data at the current time step
    Vector3f delAngCorrection;      // correction applied to delta angles used by output observer to track the EKF
    Vector3f delVelCorrection;      // correction applied to earth frame delta velocities used by output observer to track the EKF
    Vector3f velCorrection;         // correction applied to velocities used by the output observer to track the EKF
    float innovYaw;                 // compass yaw angle innovation (rad)
    uint32_t timeTasReceived_ms;    // time last TAS data was received (msec)
    bool gpsGoodToAlign;            // true when the GPS quality can be used to initialise the navigation system
    uint32_t magYawResetTimer_ms;   // timer in msec used to track how long good magnetometer data is failing innovation consistency checks
    bool consistentMagData;         // true when the magnetometers are passing consistency checks
    bool motorsArmed;               // true when the motors have been armed
    bool prevMotorsArmed;           // value of motorsArmed from previous frame
    bool posVelFusionDelayed;       // true when the position and velocity fusion has been delayed
    bool optFlowFusionDelayed;      // true when the optical flow fusion has been delayed
    bool airSpdFusionDelayed;       // true when the air speed fusion has been delayed
    bool sideSlipFusionDelayed;     // true when the sideslip fusion has been delayed

    // variables used to calulate a vertical velocity that is kinematically consistent with the verical position
    float posDownDerivative;        // Rate of chage of vertical position (dPosD/dt) in m/s. This is the first time derivative of PosD.
    float posDown;                  // Down position state used in calculation of posDownRate

    // variables used by the pre-initialisation GPS checks
    struct Location gpsloc_prev;    // LLH location of previous GPS measurement
    uint32_t lastPreAlignGpsCheckTime_ms;   // last time in msec the GPS quality was checked during pre alignment checks
    float gpsDriftNE;               // amount of drift detected in the GPS position during pre-flight GPs checks
    float gpsVertVelFilt;           // amount of filterred vertical GPS velocity detected durng pre-flight GPS checks
    float gpsHorizVelFilt;          // amount of filtered horizontal GPS velocity detected during pre-flight GPS checks

    // variable used by the in-flight GPS quality check
    bool gpsSpdAccPass;             // true when reported GPS speed accuracy passes in-flight checks
    bool ekfInnovationsPass;        // true when GPS innovations pass in-flight checks
    float sAccFilterState1;         // state variable for LPF applid to reported GPS speed accuracy
    float sAccFilterState2;         // state variable for peak hold filter applied to reported GPS speed
    uint32_t lastGpsCheckTime_ms;   // last time in msec the GPS quality was checked
    uint32_t lastInnovPassTime_ms;  // last time in msec the GPS innovations passed
    uint32_t lastInnovFailTime_ms;  // last time in msec the GPS innovations failed
    bool gpsAccuracyGood;           // true when the GPS accuracy is considered to be good enough for safe flight.

    // monitoring IMU quality
    float imuNoiseFiltState0;       // peak hold noise estimate for IMU 0
    float imuNoiseFiltState1;       // peak hold noise estimate for IMU 1
    Vector3f accelDiffFilt;         // filtered difference between IMU 0 and 1
    enum ImuSwitchState {
        IMUSWITCH_MIXED=0,          // IMU 0 & 1 are mixed
        IMUSWITCH_IMU0,             // only IMU 0 is used
        IMUSWITCH_IMU1              // only IMU 1 is used
    };
    ImuSwitchState lastImuSwitchState;  // last switch state (see imuSwitchState enum)

    // States used for unwrapping of compass yaw error
    float innovationIncrement;
    float lastInnovation;

    // variables added for optical flow fusion
    of_elements storedOF[OBS_BUFFER_LENGTH];    // OF data buffer
    of_elements ofDataNew;          // OF data at the current time horizon
    of_elements ofDataDelayed;      // OF data at the fusion time horizon
    uint8_t ofStoreIndex;           // OF data storage index
    bool newDataFlow;               // true when new optical flow data has arrived
    bool flowDataValid;             // true while optical flow data is still fresh
    bool fuseOptFlowData;           // this boolean causes the last optical flow measurement to be fused
    float auxFlowObsInnov;          // optical flow rate innovation from 1-state terrain offset estimator
    float auxFlowObsInnovVar;       // innovation variance for optical flow observations from 1-state terrain offset estimator
    Vector2 flowRadXYcomp;          // motion compensated optical flow angular rates(rad/sec)
    Vector2 flowRadXY;              // raw (non motion compensated) optical flow angular rates (rad/sec)
    uint32_t flowValidMeaTime_ms;   // time stamp from latest valid flow measurement (msec)
    uint32_t rngValidMeaTime_ms;    // time stamp from latest valid range measurement (msec)
    uint32_t flowMeaTime_ms;        // time stamp from latest flow measurement (msec)
    uint32_t gndHgtValidTime_ms;    // time stamp from last terrain offset state update (msec)
    Vector3f omegaAcrossFlowTime;   // body angular rates averaged across the optical flow sample period
    Matrix3f Tnb_flow;              // transformation matrix from nav to body axes at the middle of the optical flow sample period
    Matrix3f Tbn_flow;              // transformation matrix from body to nav axes at the middle of the optical flow sample period
    Vector2 varInnovOptFlow;        // optical flow innovations variances (rad/sec)^2
    Vector2 innovOptFlow;           // optical flow LOS innovations (rad/sec)
    float Popt;                     // Optical flow terrain height state covariance (m^2)
    float terrainState;             // terrain position state (m)
    float prevPosN;                 // north position at last measurement
    float prevPosE;                 // east position at last measurement
    bool fuseRngData;               // true when fusion of range data is demanded
    float varInnovRng;              // range finder observation innovation variance (m^2)
    float innovRng;                 // range finder observation innovation (m)
    float rngMea;                   // range finder measurement (m)
    bool inhibitGndState;           // true when the terrain position state is to remain constant
    uint32_t prevFlowFuseTime_ms;   // time both flow measurement components passed their innovation consistency checks
    Vector2 flowTestRatio;          // square of optical flow innovations divided by fail threshold used by main filter where >1.0 is a fail
    float auxFlowTestRatio;         // sum of squares of optical flow innovation divided by fail threshold used by 1-state terrain offset estimator
    float R_LOS;                    // variance of optical flow rate measurements (rad/sec)^2
    float auxRngTestRatio;          // square of range finder innovations divided by fail threshold used by main filter where >1.0 is a fail
    Vector2f flowGyroBias;          // bias error of optical flow sensor gyro output
    bool newDataRng;                // true when new valid range finder data has arrived.
    Vector2f heldVelNE;             // velocity held when no aiding is available
    enum AidingMode {AID_ABSOLUTE=0,    // GPS aiding is being used (optical flow may also be used) so position estimates are absolute.
                     AID_NONE=1,       // no aiding is being used so only attitude and height estimates are available. Either constVelMode or constPosMode must be used to constrain tilt drift.
                     AID_RELATIVE=2    // only optical flow aiding is being used so position estimates will be relative
                    };
    AidingMode PV_AidingMode;           // Defines the preferred mode for aiding of velocity and position estimates from the INS
    bool gndOffsetValid;            // true when the ground offset state can still be considered valid
    Vector3f delAngBodyOF;          // bias corrected delta angle of the vehicle IMU measured summed across the time since the last OF measurement
    float delTimeOF;                // time that delAngBodyOF is summed across

    // Range finder
    float baroHgtOffset;            // offset applied when baro height used as a backup height reference if range-finder fails
    float rngOnGnd;                 // Expected range finder reading in metres when vehicle is on ground
    float storedRngMeas[3];             // Ringbuffer of stored range measurements
    uint32_t storedRngMeasTime_ms[3];   // Ringbuffer of stored range measurement times
    uint32_t lastRngMeasTime_ms;        // Timestamp of last range measurement
    uint8_t rngMeasIndex;               // Current range measurement ringbuffer index

    // Movement detector
    bool takeOffDetected;           // true when takeoff for optical flow navigation has been detected
    float rngAtStartOfFlight;       // range finder measurement at start of flight
    uint32_t timeAtArming_ms;       // time in msec that the vehicle armed

    // baro ground effect
    bool expectGndEffectTakeoff;      // external state from ArduCopter - takeoff expected
    uint32_t takeoffExpectedSet_ms;   // system time at which expectGndEffectTakeoff was set
    bool expectGndEffectTouchdown;    // external state from ArduCopter - touchdown expected
    uint32_t touchdownExpectedSet_ms; // system time at which expectGndEffectTouchdown was set
    float meaHgtAtTakeOff;            // height measured at commencement of takeoff

    // flags indicating severw numerical errors in innovation variance calculation for different fusion operations
    struct {
        bool bad_xmag:1;
        bool bad_ymag:1;
        bool bad_zmag:1;
        bool bad_airspeed:1;
        bool bad_sideslip:1;
    } faultStatus;

    // flags indicating which GPS quality checks are failing
    struct {
        bool bad_sAcc:1;
        bool bad_hAcc:1;
        bool bad_yaw:1;
        bool bad_sats:1;
        bool bad_VZ:1;
        bool bad_horiz_drift:1;
        bool bad_hdop:1;
        bool bad_vert_vel:1;
        bool bad_fix:1;
        bool bad_horiz_vel:1;
    } gpsCheckStatus;

    // states held by magnetomter fusion across time steps
    // magnetometer X,Y,Z measurements are fused across three time steps
    // to level computational load as this is an expensive operation
    struct {
        ftype q0;
        ftype q1;
        ftype q2;
        ftype q3;
        ftype magN;
        ftype magE;
        ftype magD;
        ftype magXbias;
        ftype magYbias;
        ftype magZbias;
        uint8_t obsIndex;
        Matrix3f DCM;
        Vector3f MagPred;
        ftype R_MAG;
        Vector9 SH_MAG;
    } mag_state;


    // string representing last reason for prearm failure
    char prearm_fail_string[40];

    // performance counters
    AP_HAL::Util::perf_counter_t  _perf_UpdateFilter;
    AP_HAL::Util::perf_counter_t  _perf_CovariancePrediction;
    AP_HAL::Util::perf_counter_t  _perf_FuseVelPosNED;
    AP_HAL::Util::perf_counter_t  _perf_FuseMagnetometer;
    AP_HAL::Util::perf_counter_t  _perf_FuseAirspeed;
    AP_HAL::Util::perf_counter_t  _perf_FuseSideslip;
    AP_HAL::Util::perf_counter_t  _perf_TerrainOffset;
    AP_HAL::Util::perf_counter_t  _perf_FuseOptFlow;
    AP_HAL::Util::perf_counter_t  _perf_test[10];

    // should we assume zero sideslip?
    bool assume_zero_sideslip(void) const;

    // vehicle specific initial gyro bias uncertainty
    float InitialGyroBiasUncertainty(void) const;
};

#endif // AP_NavEKF2_core
